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GOE 397 AIRFOIL (goe397-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 397 AIRFOIL (goe397-il)
Reynolds number: 200,000
Max Cl/Cd: 79.12 at α=4°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe397-il-200000-n5.txt
Download as CSV file: xf-goe397-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 397 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3829   0.09684   0.09340  -0.0237   1.0000   0.0169
  -7.750  -0.3799   0.09354   0.09014  -0.0245   1.0000   0.0169
  -7.500  -0.3767   0.08883   0.08546  -0.0233   1.0000   0.0164
  -7.250  -0.3722   0.08515   0.08178  -0.0224   1.0000   0.0156
  -7.000  -0.3679   0.08199   0.07866  -0.0236   1.0000   0.0151
  -6.750  -0.3625   0.07882   0.07553  -0.0253   1.0000   0.0148
  -6.500  -0.3557   0.07552   0.07226  -0.0273   1.0000   0.0148
  -6.250  -0.3454   0.07189   0.06865  -0.0309   1.0000   0.0158
  -6.000  -0.3378   0.06869   0.06548  -0.0322   1.0000   0.0155
  -5.750  -0.3078   0.06312   0.05983  -0.0406   0.9939   0.0161
  -5.500  -0.2741   0.05744   0.05405  -0.0483   0.9852   0.0161
  -5.250  -0.2375   0.05155   0.04800  -0.0558   0.9765   0.0162
  -5.000  -0.1981   0.04485   0.04108  -0.0634   0.9668   0.0172
  -4.750  -0.1745   0.04425   0.04048  -0.0647   0.9572   0.0193
  -4.500  -0.1398   0.04038   0.03640  -0.0691   0.9474   0.0209
  -4.250  -0.1027   0.03568   0.03140  -0.0734   0.9379   0.0220
  -4.000  -0.0656   0.03099   0.02630  -0.0766   0.9271   0.0253
  -3.750  -0.0305   0.02616   0.02084  -0.0783   0.9159   0.0275
  -3.500  -0.0032   0.02426   0.01878  -0.0797   0.9041   0.0299
  -3.250   0.0262   0.02286   0.01714  -0.0805   0.8925   0.0336
  -3.000   0.0558   0.02038   0.01417  -0.0807   0.8814   0.0349
  -2.750   0.0847   0.01896   0.01232  -0.0806   0.8704   0.0375
  -2.500   0.1123   0.01765   0.01063  -0.0804   0.8593   0.0381
  -2.250   0.1395   0.01648   0.00914  -0.0801   0.8486   0.0384
  -2.000   0.1666   0.01570   0.00806  -0.0797   0.8381   0.0388
  -1.500   0.2195   0.01356   0.00552  -0.0790   0.8183   0.0411
  -1.250   0.2459   0.01305   0.00491  -0.0786   0.8088   0.0422
  -1.000   0.2723   0.01274   0.00453  -0.0782   0.7993   0.0450
  -0.750   0.2983   0.01237   0.00409  -0.0777   0.7874   0.0459
  -0.500   0.3240   0.01200   0.00364  -0.0771   0.7738   0.0456
  -0.250   0.3495   0.01170   0.00326  -0.0764   0.7595   0.0453
   0.000   0.3752   0.01145   0.00296  -0.0758   0.7469   0.0452
   0.250   0.4013   0.01125   0.00273  -0.0754   0.7365   0.0452
   0.500   0.4275   0.01111   0.00254  -0.0749   0.7273   0.0454
   0.750   0.4539   0.01100   0.00239  -0.0745   0.7178   0.0458
   1.000   0.4803   0.01094   0.00229  -0.0741   0.7088   0.0466
   1.500   0.5332   0.01087   0.00218  -0.0733   0.6912   0.0503
   1.750   0.5595   0.01083   0.00218  -0.0729   0.6829   0.0611
   2.000   0.6041   0.00893   0.00233  -0.0770   0.6743   1.0000
   2.250   0.6301   0.00905   0.00242  -0.0766   0.6654   1.0000
   2.500   0.6561   0.00918   0.00251  -0.0761   0.6569   1.0000
   2.750   0.6820   0.00931   0.00264  -0.0756   0.6465   1.0000
   3.000   0.7072   0.00947   0.00275  -0.0749   0.6313   1.0000
   3.250   0.7321   0.00963   0.00289  -0.0742   0.6131   1.0000
   3.500   0.7569   0.00979   0.00305  -0.0734   0.5926   1.0000
   3.750   0.7814   0.00996   0.00320  -0.0726   0.5676   1.0000
   4.000   0.8046   0.01017   0.00332  -0.0716   0.5201   1.0000
   4.250   0.8257   0.01059   0.00348  -0.0702   0.4527   1.0000
   4.500   0.8466   0.01115   0.00379  -0.0690   0.3983   1.0000
   4.750   0.8678   0.01176   0.00421  -0.0678   0.3460   1.0000
   5.000   0.8875   0.01255   0.00471  -0.0666   0.2682   1.0000
   5.500   0.9196   0.01528   0.00638  -0.0636   0.0720   1.0000
   5.750   0.9413   0.01593   0.00702  -0.0627   0.0564   1.0000
   6.000   0.9631   0.01655   0.00769  -0.0618   0.0441   1.0000
   6.250   0.9838   0.01732   0.00842  -0.0607   0.0306   1.0000
   6.500   1.0042   0.01813   0.00931  -0.0595   0.0223   1.0000
   6.750   1.0233   0.01907   0.01035  -0.0581   0.0184   1.0000
   7.000   1.0417   0.02012   0.01154  -0.0566   0.0163   1.0000
   7.250   1.0592   0.02129   0.01284  -0.0550   0.0147   1.0000
   7.500   1.0760   0.02258   0.01424  -0.0534   0.0130   1.0000
   7.750   1.0882   0.02500   0.01680  -0.0511   0.0112   1.0000
   8.000   1.1068   0.02656   0.01856  -0.0497   0.0107   1.0000
   8.250   1.1252   0.02848   0.02077  -0.0482   0.0103   1.0000
   8.500   1.1431   0.03075   0.02332  -0.0468   0.0099   1.0000
   8.750   1.1593   0.03337   0.02628  -0.0452   0.0095   1.0000
   9.000   1.1737   0.03571   0.02893  -0.0435   0.0090   1.0000
   9.250   1.1861   0.03790   0.03139  -0.0418   0.0085   1.0000
   9.500   1.1973   0.03924   0.03287  -0.0402   0.0078   1.0000
   9.750   1.2042   0.04130   0.03511  -0.0383   0.0074   1.0000
  10.000   1.2043   0.04460   0.03874  -0.0358   0.0072   1.0000
  10.250   1.1985   0.04801   0.04247  -0.0327   0.0072   1.0000
  10.500   1.1871   0.05135   0.04610  -0.0294   0.0071   1.0000
  11.000   1.0756   0.04958   0.04507  -0.0199   0.0073   1.0000
  11.250   1.0554   0.05484   0.05056  -0.0196   0.0073   1.0000
  11.500   1.0338   0.06080   0.05674  -0.0202   0.0074   1.0000
  11.750   1.0106   0.06750   0.06365  -0.0218   0.0074   1.0000
  12.000   0.9842   0.07527   0.07163  -0.0244   0.0075   1.0000
  12.250   0.9543   0.08429   0.08087  -0.0284   0.0077   1.0000
  12.500   0.9210   0.09484   0.09161  -0.0341   0.0079   1.0000
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